CN107963202B - Small long-endurance fixed-wing unmanned aerial vehicle power supply controller system and operation method - Google Patents
Small long-endurance fixed-wing unmanned aerial vehicle power supply controller system and operation method Download PDFInfo
- Publication number
- CN107963202B CN107963202B CN201711312208.7A CN201711312208A CN107963202B CN 107963202 B CN107963202 B CN 107963202B CN 201711312208 A CN201711312208 A CN 201711312208A CN 107963202 B CN107963202 B CN 107963202B
- Authority
- CN
- China
- Prior art keywords
- voltage
- power supply
- module
- unmanned aerial
- aerial vehicle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C19/00—Aircraft control not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D2221/00—Electric power distribution systems onboard aircraft
Abstract
The invention provides a power supply controller system of a small-sized long-endurance fixed-wing unmanned aerial vehicle and an operation method thereof, wherein the power supply controller system comprises a rectification voltage-stabilizing module, a three-phase rectification bridge is utilized to convert three-phase alternating current generated by a generator into direct current required by airborne electronic control equipment of the unmanned aerial vehicle, and the voltage is stabilized in a certain range; the interval power generation module comprises a frequency-to-voltage module and a voltage-to-switching value module, and jointly controls and determines whether the engine generates power in different frequency interval sections; and the power supply switching module is used for realizing switching of power supply sources of unmanned aerial vehicle airborne equipment. The invention aims to supply power to an onboard electric control device by utilizing the power generation of an engine, meanwhile, the control of a complex single chip microcomputer is not required to be introduced, the rotating speed of the engine can be distinguished only through hardware design, the power supply in a proper interval can be realized, and the smooth conversion between the power supply of a storage battery pack and the power supply of a generator is realized.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a design system and an operation method of a power supply controller of a small long-endurance fixed-wing unmanned aerial vehicle.
Background
With the progress of unmanned aerial vehicle technology, small unmanned aerial vehicle has been widely used in fields such as frontier defense patrol, aerial photography, logistics distribution, military investigation, etc. Unmanned aerial vehicle duration exceeds 24 hours and is called long-endurance unmanned aerial vehicle, and long-endurance unmanned aerial vehicle is generally used for executing strategic or battle reconnaissance tasks, has durable information collection and battlefield monitoring capability, and can be used as an unmanned combat platform, so that the unmanned aerial vehicle is an important point for the development of weaponry in various countries.
The factor that restricts unmanned aerial vehicle long endurance is the power supply problem of unmanned aerial vehicle airborne electrical control equipment in addition to the power aspect, and most unmanned aerial vehicles still adopt single storage battery's power supply scheme at present, and storage battery's density is very big, and it is very unreasonable to adorn on small-size long endurance unmanned aerial vehicle, in addition in case storage battery breaks down, must lead to serious result. In addition, although some companies propose to utilize the unmanned aerial vehicle engine to generate electricity to supply power for the onboard electronic control equipment, fewer people consider the switching problem of the storage battery pack and the generator circuit, and more unmanned aerial vehicle engines are not suitable to divide extra power to supply power for the onboard electronic control equipment under idle working conditions and full power output.
Disclosure of Invention
The invention aims to: in order to overcome the defects in the prior art, the invention provides a power supply controller system of a small-sized long-endurance fixed-wing unmanned aerial vehicle and an operation method thereof, and mainly aims to solve or improve the endurance of the unmanned aerial vehicle from the power supply problem of unmanned aerial vehicle electric control equipment, and the power supply controller is developed, can utilize the self engine of the unmanned aerial vehicle to generate power for the electric control equipment and reasonably solve the problem of switching between a storage battery pack and a generator circuit.
The technical scheme is as follows: in order to achieve the above purpose, the invention adopts the following technical scheme:
the utility model provides a small-size long dead wing unmanned aerial vehicle power supply controller system that keeps down, includes rectification steady voltage module, interval power generation module and power switch module, wherein:
the unmanned aerial vehicle engine is respectively connected with a generator and the interval power generation module, and is respectively connected with the rectifying and voltage stabilizing module, and the interval power generation module controls whether the engine generates power in different frequency interval sections;
the rectification voltage stabilizing module is connected with a power supply switching module, and the power supply switching module controls the on-board equipment to be connected with the storage battery pack power supply module or the rectification voltage stabilizing module so as to realize switching of power supply sources of the unmanned aerial vehicle on-board equipment.
Further, the interval power generation module sequentially comprises a frequency-to-voltage module and a voltage-to-switching value module, and the functions of determining whether the engine generates power in different frequency interval sections are controlled together.
Further, the frequency-to-voltage module is provided with a frequency/voltage converter.
Furthermore, the rectification voltage stabilizing module converts three-phase alternating current generated by the generator into direct current required by unmanned aerial vehicle airborne equipment by utilizing a three-phase rectification bridge, and stabilizes output voltage by 30-55V, output current by 16.8-20A and withstand voltage by 100V.
According to the running method of the power supply controller system of the small long-endurance fixed-wing unmanned aerial vehicle, whether the power supply controller system is suitable for a generator to generate electricity at the rotating speed of the engine is judged according to the rotating speed of the engine, and accordingly, the power generation in a corresponding interval is realized, so that the engine is stable in running; the method comprises the following specific steps:
1) The unmanned aerial vehicle flight is divided into a take-off stage under a high-speed full-load/overload working condition, a cruising stage under an intermediate-speed working condition and a landing stage under a low-speed idling working condition;
2) The interval power generation module is used for obtaining a switching value signal through processing voltage signals generated by the engine at different rotational speeds at different stages, and controlling the power supply switching module according to the switching value signal;
3) The interval power generation module divides a power generation interval into: no power is generated under the high-rotation speed full-load/overload working condition and the low-rotation speed idle working condition; generating electricity under the working condition of the middle rotating speed;
4) The power supply switching module controls and determines the power supply source of unmanned aerial vehicle airborne equipment: the generator supplies power to the onboard electronic control equipment in the cruising phase interval of the intermediate rotating speed, and the storage battery pack supplies power to the onboard electronic control equipment in the interval of low-rotating-speed idling or high-rotating-speed full load/overload.
Further, the specific method of the step 1) is as follows: the frequency-to-voltage conversion module of the interval power generation module collects pulse frequency signals of the engine rotating speed by using a frequency-to-voltage converter, and converts the pulse frequency signals into voltage signals according to the proportional relation of output voltage and input frequency; the voltage conversion switching value module converts the voltage signals converted according to the proportion into switching value signals according to the requirement and transmits the switching value signals to the power supply switching module.
Further, the specific method of the step 2) is as follows: when the voltage signal U in ＜U R1 Or U (U) in ＞U R2 When U O Output low level U OL The enabling end of the rectifying and voltage stabilizing module is low-level and does not work, so that the power supply switching module receives a low-level signal, a storage battery pack supplies power for unmanned aerial vehicle-mounted equipment, and a generator does not work;
when U is R1 ＜U in ＜U R2 When U O Output high level U OH The energy end of the rectifying and voltage stabilizing module is in a high level and is in a working state, and the power supply switching module receives a high level signal to enable the generator to supply power to unmanned aerial vehicle-mounted equipment, and the generator works at the moment;
wherein U is R1 Is the lower limit value of the voltage, U R2 As the upper limit value of the voltage, U O For outputting a level signal.
Further, the power level of the engine of the unmanned aerial vehicle is 4kw, and the corresponding intermediate rotating speed is 2500 rpm-5500 rpm.
The beneficial effects are that: compared with the prior art, the power supply controller system and the operation method of the small long-endurance fixed-wing unmanned aerial vehicle provided by the invention have the following advantages: aiming at the defects of the prior art, the invention provides the power supply controller which directly utilizes hardware to distinguish the rotation speed of the engine and realize power generation in a proper interval without introducing a singlechip and other complex control mechanisms in consideration of the fact that the engine of the unmanned aerial vehicle is not suitable for separating extra power to provide power for an onboard electric control device under idle working condition and full power output even overload, so that the problem of long-endurance of the unmanned aerial vehicle can be well solved, meanwhile, the structure is compact, unnecessary equipment is not needed, the unmanned aerial vehicle can be well applied to the unmanned aerial vehicle in small-sized long-endurance, and the application field of the unmanned aerial vehicle is widened.
Drawings
Fig. 1 is a frequency-voltage conversion diagram of LM 331.
Fig. 2 is a graph of LM339 dual threshold voltage comparison.
Fig. 3 is an overall schematic diagram of a power control system.
Fig. 4 is a plot of data for a specific example experiment.
Detailed Description
The invention provides a power supply controller system of a small-sized long-endurance fixed-wing unmanned aerial vehicle and an operation method thereof, wherein the power supply controller system comprises a rectification voltage-stabilizing module, a three-phase rectification bridge is utilized to convert three-phase alternating current generated by a generator into direct current required by airborne electronic control equipment of the unmanned aerial vehicle, and the voltage is stabilized in a certain range; the interval power generation module comprises a frequency-to-voltage module and a voltage-to-switching value module, and jointly controls and determines whether the engine generates power in different frequency interval sections; and the power supply switching module is used for realizing switching of power supply sources of unmanned aerial vehicle airborne equipment. The invention aims to supply power to an onboard electric control device by utilizing the power generation of an engine, meanwhile, the control of a complex single chip microcomputer is not required to be introduced, the rotating speed of the engine can be distinguished only through hardware design, the power supply in a proper interval can be realized, and the smooth conversion between the power supply of a storage battery pack and the power supply of a generator is realized.
The invention relates to a design of a power supply controller of a small-sized long-endurance fixed-wing unmanned aerial vehicle, which is shown in fig. 3 and comprises a rectifying and voltage stabilizing module, an interval power generation module and a power supply switching module.
The rectification voltage stabilizing module converts three-phase alternating current generated by the generator into direct current required by unmanned aerial vehicle onboard electric control equipment by utilizing a three-phase rectification bridge, and voltage stabilizing output voltage is 30-55V, output current is 16.8-20A and withstand voltage is 100V by combining the electricity utilization characteristic of the unmanned aerial vehicle onboard electric control equipment;
the interval power generation module comprises a frequency-to-voltage conversion module and a voltage-to-switching value conversion module. Because the unmanned aerial vehicle is roughly divided into three processes from take-off to landing, namely a take-off stage, a cruising stage and a landing stage. In the take-off stage, in order to generate the power which the unmanned aerial vehicle should take off, the engine speed is increased sharply from 0rpm, and the engine power is used for conveying the power, so that the power generation is not suitable; in the landing stage, the rotation speed of the engine of the unmanned aerial vehicle is rapidly reduced, so that the conditions such as instability and the like are very easy to generate, and the power generation is not suitable at the moment; in the cruising stage, the engine operates more stably, a part of power can be separated to be used for power generation, namely, the unmanned aerial vehicle engine is not suitable for power generation under the working condition of low rotation speed and idle speed and under the condition of high rotation speed and full load even overload, only the power can be generated at the middle rotation speed, and the interval power generation module provides the functions of distinguishing the rotation speed of the engine only through hardware and dividing the power generation interval to generate power in the rotation speed interval suitable for power generation on the premise that no complex control mechanism such as a singlechip is introduced. The frequency-to-voltage module directly collects the engine rotating speed pulse signals by using a frequency/voltage converter and converts the pulse frequency into voltage signals in proportion. The voltage-to-switching value module converts the voltage signals converted in proportion into switching values according to requirements. The frequency-to-voltage conversion module and the voltage-to-switching value conversion module realize the function that the interval power generation module controls whether the engine generates power in different frequency interval sections.
The power supply switching module determines whether the unmanned aerial vehicle-mounted equipment is powered by the storage battery or the generator, and can supply power to the unmanned aerial vehicle-mounted electronic control equipment by the generator in a cruising interval, and supply power to the unmanned aerial vehicle-mounted electronic control equipment by the storage battery in an idling or super-power interval, so that the unmanned aerial vehicle-mounted electronic control equipment can be smoothly switched.
The invention will be further described with reference to the drawings and examples.
Examples
The unmanned aerial vehicle is roughly divided into three processes from taking off to landing, namely a taking-off stage, a cruising stage and a landing stage. Taking the unmanned aerial vehicle engine power level as an example, the rotating speed range is between 0rpm and 7500rpm, the engine is in an idle state in the range of 0rpm and 2500rpm, the unmanned aerial vehicle engine is unstable, the unmanned aerial vehicle is unfavorable for power generation, the engine is already in overload operation in the range of 5500rpm to 7500rpm, and at the moment, a part of power is not suitable to be separated for power generation, so that the engine power range suitable for power generation is 2500rpm to 5500rpm.
As shown in fig. 1 (a) and (b), the interval power generation module adopts a frequency/voltage converter LM331 to directly collect the engine speed pulse signal, and converts the pulse frequency into a voltage signal in proportion; then, the voltage signals converted in proportion are converted into switching values according to the requirement by using an LM339 dual-threshold voltage comparator, as shown in fig. 2 (a) and (b), U R1 Is the lower limit value of the voltage (namely the lower limit of the engine speed interval capable of allowing power generation), U R2 Is the upper limit value of the voltage (namely the upper limit of the engine speed interval which can allow power generation), when U in ＜U R1 Or U (U) in ＞U R2 ，U O Output low level U OL The enabling end of the rectifying and voltage stabilizing module is low-level and does not work, so that the power supply switching module receives a low-level signal to enable the storage battery pack to supply power to unmanned aerial vehicle-mounted equipment, and the generator does not work.
When U is R1 ＜U in ＜U R2 When U O Output high level U OH The power supply switching module receives a high-level signal to enable the generator to supply power to unmanned aerial vehicle-mounted equipment, the generator works at the moment, the rectifying and voltage-stabilizing module converts three-phase alternating current generated by the generator into direct current required by the unmanned aerial vehicle-mounted electronic control equipment through a three-phase rectifying bridge, and voltage-stabilizing output voltage is 30-55V, output current is 16.8-20A and withstand voltage is 100V according to the electricity utilization characteristics of the unmanned aerial vehicle-mounted electronic control equipment.
The power supply switching module determines the level of the enabling end of the rectifying and voltage stabilizing module according to the voltage signal output by the LM339 in the interval power generation module and determines whether the rectifying and voltage stabilizing module works or not; and then through the LTC4416 chip in the power switching module, whether the unmanned aerial vehicle onboard equipment is powered by a storage battery or a generator is determined, so that the unmanned aerial vehicle onboard electronic control equipment can be powered by the generator in the cruising interval, and the unmanned aerial vehicle onboard electronic control equipment can be powered by the storage battery in the idling or super-power interval, so that the unmanned aerial vehicle onboard electronic control equipment can be smoothly switched.
Specific experimental examples of the method of the invention: when the load of the on-board power supply equipment is 5 ohms, a proper power generation interval is selected to be between 2500rpm and 5500rpm of the engine, the power generation power of the generator is measured, the obtained experimental data are shown in table 1, and the experimental data are drawn into fig. 4, wherein the power generation power of the generator is 0 when the engine speed is lower than 2500rpm or higher than 5500rpm, namely, no power is generated; in the middle rotating speed interval, the generator generates corresponding power and changes along with the change of the rotating speed.
Table 1 generator power for intermediate speed interval
| Engine speed/rpm | 2500 | 3000 | 3500 | 4000 | 4500 | 5000 | 5500 |
| Generating power/w of generator | 94.8456 | 133.8970 | 176.3412 | 226.118 | 274.896 | 323.424 | 381.5596 |
The foregoing is only a preferred embodiment of the invention, it being noted that: it will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the principles of the present invention, and such modifications and adaptations are intended to be comprehended within the scope of the invention.
Claims (4)
1. An operation method of a power supply controller system of a small long-endurance fixed-wing unmanned aerial vehicle is characterized by comprising the following steps of: the system comprises a rectifying and voltage stabilizing module, an interval power generation module and a power supply switching module, wherein:
the unmanned aerial vehicle engine is respectively connected with a generator and the interval power generation module, and is respectively connected with the rectifying and voltage stabilizing module, and the interval power generation module controls whether the engine generates power in different frequency interval sections;
the rectification voltage-stabilizing module is connected with a power supply switching module, and the power supply switching module controls the on-board equipment to be connected with the storage battery pack power supply module or the rectification voltage-stabilizing module so as to realize switching of power supply sources of the unmanned aerial vehicle on-board equipment;
the interval power generation module sequentially comprises a frequency-to-voltage module and a voltage-to-switching value module, and jointly controls the function of determining whether the engine generates power in different frequency interval sections;
judging whether the engine is suitable for the generator to generate electricity or not according to the rotation speed of the engine, and generating electricity in a corresponding interval according to the rotation speed of the engine so as to ensure that the engine operates stably; the method comprises the following specific steps:
1) The unmanned aerial vehicle flight is divided into a take-off stage under a high-speed full-load/overload working condition, a cruising stage under an intermediate-speed working condition and a landing stage under a low-speed idling working condition;
2) The interval power generation module converts the different rotation speeds of the engine at different stages into voltage signals, the voltage signals are processed to obtain switching value signals, and the power supply switching module is controlled according to the switching value signals;
3) The interval power generation module divides a power generation interval into: no power is generated under the high-rotation speed full-load/overload working condition and the low-rotation speed idle working condition; generating electricity under the working condition of the middle rotating speed;
4) The power supply switching module controls and determines the power supply source of unmanned aerial vehicle airborne equipment: the generator supplies power to the onboard electronic control equipment in the cruising phase interval of the intermediate rotating speed, and the storage battery pack supplies power to the onboard electronic control equipment in the interval of low-rotating-speed idling or high-rotating-speed full load/overload.
2. The method of operating a power controller system for a small, long-endurance, fixed-wing unmanned aerial vehicle of claim 1, wherein: the specific method of the step 1) is as follows: the frequency-to-voltage conversion module of the interval power generation module collects pulse frequency signals of the engine rotating speed by using a frequency-to-voltage converter, and converts the pulse frequency signals into voltage signals according to the proportional relation that the output voltage is proportional to the input frequency; the voltage-to-switching value module converts the voltage signals converted according to the proportion relationship into switching value signals according to the requirement and transmits the switching value signals to the power supply switching module.
3. The method of operating a power controller system for a small, long-endurance, fixed-wing unmanned aerial vehicle of claim 1, wherein: the specific method of the step 2) is as follows: when the voltage signal U in ＜U R1 Or U (U) in ＞U R2 When U O Output low level U OL The enabling end of the rectifying and voltage stabilizing module is low-level and does not work, so that the power supply switching module receives a low-level signal, a storage battery pack supplies power for unmanned aerial vehicle-mounted equipment, and a generator does not work;
when U is R1 ＜U in ＜U R2 When U O Output high level U OH The energy end of the rectifying and voltage stabilizing module is in a high level and is in a working state, and the power supply switching module receives a high level signal to enable the generator to supply power to unmanned aerial vehicle-mounted equipment, and the generator works at the moment;
wherein U is R1 Is the lower limit value of the voltage, U R2 As the upper limit value of the voltage, U O For outputting a level signal.
4. The method of operating a power controller system for a small, long-endurance, fixed-wing unmanned aerial vehicle of claim 1, wherein: the power level of the engine of the unmanned aerial vehicle is 4kw, and the corresponding intermediate rotating speed is 2500 rpm-5500 rpm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711312208.7A CN107963202B (en) | 2017-12-07 | 2017-12-07 | Small long-endurance fixed-wing unmanned aerial vehicle power supply controller system and operation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711312208.7A CN107963202B (en) | 2017-12-07 | 2017-12-07 | Small long-endurance fixed-wing unmanned aerial vehicle power supply controller system and operation method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107963202A CN107963202A (en) | 2018-04-27 |
| CN107963202B true CN107963202B (en) | 2023-09-26 |
Family
ID=61994357
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711312208.7A Active CN107963202B (en) | 2017-12-07 | 2017-12-07 | Small long-endurance fixed-wing unmanned aerial vehicle power supply controller system and operation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107963202B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109850188B (en) * | 2018-12-12 | 2020-10-23 | 上海航天控制技术研究所 | Flywheel speed stabilization control system based on frequency-voltage conversion |
| CN113815872A (en) * | 2021-08-31 | 2021-12-21 | 北京航空航天大学苏州创新研究院 | High-endurance high-bearing rotor unmanned aerial vehicle |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103460585A (en) * | 2011-03-17 | 2013-12-18 | 伊斯帕诺-絮扎公司 | Electrical energy supply of aircraft |
| CN105471069A (en) * | 2016-01-05 | 2016-04-06 | 海鹰航空通用装备有限责任公司 | Vehicle-mounted power supply management and control system and equipment for small-sized unmanned aerial vehicle |
| CN107219794A (en) * | 2017-06-13 | 2017-09-29 | 长沙灵动航空科技有限公司 | A kind of long endurance unmanned aircraft oil-electricity system voltage hand control method for automatically switching and control device |
| CN107399439A (en) * | 2016-05-18 | 2017-11-28 | 空中客车西班牙运营有限责任公司 | Electric power supply system with multiphase generator and the airborne vehicle with this electric power supply system |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8427001B2 (en) * | 2008-07-30 | 2013-04-23 | Honeywell International, Inc. | Electrically controlled frequency-based power system architecture for aircraft |
| GB201110719D0 (en) * | 2011-06-24 | 2011-08-10 | Rolls Royce Plc | Electrical system architecture and electrical power generation system |
| US10389114B2 (en) * | 2014-11-25 | 2019-08-20 | The Boeing Company | Regulated transformer rectifier unit for aircraft systems |
-
2017
- 2017-12-07 CN CN201711312208.7A patent/CN107963202B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103460585A (en) * | 2011-03-17 | 2013-12-18 | 伊斯帕诺-絮扎公司 | Electrical energy supply of aircraft |
| CN105471069A (en) * | 2016-01-05 | 2016-04-06 | 海鹰航空通用装备有限责任公司 | Vehicle-mounted power supply management and control system and equipment for small-sized unmanned aerial vehicle |
| CN107399439A (en) * | 2016-05-18 | 2017-11-28 | 空中客车西班牙运营有限责任公司 | Electric power supply system with multiphase generator and the airborne vehicle with this electric power supply system |
| CN107219794A (en) * | 2017-06-13 | 2017-09-29 | 长沙灵动航空科技有限公司 | A kind of long endurance unmanned aircraft oil-electricity system voltage hand control method for automatically switching and control device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107963202A (en) | 2018-04-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10875646B2 (en) | Hybrid-powered unmanned vehicle | |
| CN109733621B (en) | Hybrid unmanned aerial vehicle of many propulsion modes | |
| CN105711826A (en) | Tandem type oil-electric hybrid unmanned aerial vehicle | |
| CN110155344B (en) | Hybrid power unmanned helicopter energy control system and helicopter with same | |
| CN206520748U (en) | A kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle | |
| CN110001973B (en) | Hybrid propulsion system of light fixed-wing unmanned aerial vehicle and control method | |
| CN109094790B (en) | Power configuration scheme and control method for hybrid power system of helicopter | |
| CN107963202B (en) | Small long-endurance fixed-wing unmanned aerial vehicle power supply controller system and operation method | |
| CN109263485A (en) | A kind of control method and system of intelligent generator | |
| CN108454864A (en) | General-purpose aircraft series connection type hybrid power system | |
| US20220289395A1 (en) | Propulsion system for aircraft and method of manufacturing aircraft | |
| CN210882651U (en) | Hybrid power propulsion system of light-duty fixed wing unmanned aerial vehicle | |
| CN103738503B (en) | A kind of unmanned aerial vehicle onboard generating set | |
| CN110395395A (en) | Parallel operation formula multi-rotor unmanned aerial vehicle mixed power plant based on heavy oil internal combustion engine | |
| CN205811542U (en) | A kind of unmanned plane electric power system | |
| CN109687810B (en) | Rotating speed control method for preventing motor overspeed of pure electric vehicle | |
| CN111605713B (en) | Hybrid rectifying device and control method of hybrid power system of unmanned aerial vehicle | |
| CN110963050B (en) | Multi-energy hybrid propulsion power system for unmanned aerial vehicle | |
| CN207607639U (en) | A kind of small-sized long endurance fixed-wing unmanned plane Power converter system | |
| CN109018378B (en) | Oil-electricity hybrid power supply system, power generation control device and method thereof, and unmanned aerial vehicle | |
| US20230083409A1 (en) | Power system, power system control method, uav and uav control method | |
| CN111301659A (en) | Intelligent cabin ventilation system | |
| CN217805302U (en) | Oil-electricity hybrid power system for aircraft | |
| CN206402054U (en) | Power intake parallel axes electrification structure | |
| CN218877622U (en) | Novel power management module for fuel cell aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |